The design optimization of wings for supersonic transport by means of Multiobjective Evolutionary Algorithms is presented. Three objective functions are first considered to minimize the drag for transonic cruise, the drag for supersonic cruise and the bending moment at the wing root at the supersonic condition. The wing shape is defined by planform, thickness distributions and warp shapes in total of 66 design variables. A Navier-Stokes code is used to evaluate the aerodynamic performance at both cruise conditions. Based on the results, the optimization problem is further revised. The definition of the thickness distributions is given more precisely by adding control points. In total 72 design variables are used. The fourth objective function to minimize the pitching moment is added. The results of the revised optimization are compared with the three-objective optimization results as well as NAL's design. Two Pareto solutions are found superior to NAL's design for all four objective functions. The planform shapes of those solutions are Arrow wing type.
|出版ステータス||Published - 2001|
|イベント||15th AIAA Computational Fluid Dynamics Conference 2001 - Anaheim, CA, United States|
継続期間: 2001 6月 11 → 2001 6月 14
|Other||15th AIAA Computational Fluid Dynamics Conference 2001|
|Period||01/6/11 → 01/6/14|
ASJC Scopus subject areas